Shuttle-launch triangular space station

Abstract

A triangular space station deployable in orbit. The framework is comprised of three trusses, formed of a pair of generally planar faces comprised of foldable struts which expand and lock into rigid structural engagement forming a repetition of equilateral triangles and non-folding diagonal struts interconnecting the two faces. The struts are joined together by node fittings. The framework can be packaged into a size and configuration which can be transported by a space shuttle orbiter in a single orbital flight and when deployed, provides large work/construction area and ample planar surface area for solar panels and thermal radiators. A plurality of modules are secured to the framework and then joined by tunnels to comprise an interconnected modular array disposed along the free edges of the framework. Thruster units for space station orientation and altitude maintenance are provided. The triangular space station provides a structurally stable unit having sufficiently high structural integrity and natural frequency for facilitating docking, satellite servicing and launch operations.

We claim: 
     
       1. A space station deployable in earth orbit from elements transported in the payload bay of the Space Shuttle Orbiter, comprising: a structural framework formed of three rectangular, full area, planar trusses, each of said trusses comprising a plurality of structural struts, said trusses attached together to form a right polygonal body with a cross section in the form of a triangle thereby forming a very stiff structure with a high natural frequency and having a very large area for work space and attachment;   an array of solar panels firmly attached to the outside of a face of at least one of said planar trusses; and   at least one module secured to said framework.   
     
     
       2. The space station system as set forth in claim 1 wherein a plurality of said truss struts are constructed for foldable positioning, one against the other, for facilitating collapsed packaging during launch into earth orbit and the deployment therein into said structural frame. 
     
     
       3. The space station system as set forth in claim 1 wherein each truss comprises a tetrahedral having a pair of generally parallel planar faces formed of a continuous repetition of equilateral triangles generated by a plurality of struts interconnected by node fittings, said faces joined together by diagonal strut members connected to the node fittings. 
     
     
       4. The space station as set forth in claim 3 wherein said face struts are foldable and include an intermediate hinged section and biasing means for automatically unfolding said face struts about said hinge during deployment of said space station. 
     
     
       5. The space station as set forth in claim 1 wherein said modules include generally cylindrical vessels coupled one to another in pressurized communication therebetween and being secured to the apexes of said triangular structural frame. 
     
     
       6. The space station as set forth in claim 5 wherein the modules secured to an apex of said frame are connected to the modules secured to another apex of said frame by elongated tunnels extending along said frame. 
     
     
       7. The space station as set forth in claim 6 wherein each of said elongate tunnels comprise a plurality of telescoping tunnel sections sealingly connected one to the other. 
     
     
       8. The space station as set forth in claim 1 including an array of thermal radiator panels secured to another of said planar trusses. 
     
     
       9. The space station as set forth in claim 1 including thruster units for orientation and altitude maintenance. 
     
     
       10. A space station deployable in earth orbit comprising: a triangular shaped structural framework;   each side of said framework comprising a rectangular shaped truss having two generally parallel, full area, planar faces, each face formed of a continuous repetition of interconnected equilateral triangles generated by a plurality of struts interconnected by node fittings;   diagonal struts joining the two faces together;   the face struts and the diagonal struts being of approximately the same length.   
     
     
       11. The space station as set forth in claim 10 wherein the struts generating the planar faces are constructed for foldable positioning, one against the other, for facilitating collapsed packaging. 
     
     
       12. The space station as set forth in claim 11 wherein said foldable struts include biasing means for automatically unfolding said struts during deployment. 
     
     
       13. The space station as set forth in claim 10 including an array of solar panels secured to the face of one of said trusses. 
     
     
       14. The space station as set forth in claim 13 including an array of thermal radiators secured to the face of another truss. 
     
     
       15. The space station as set forth in claim 14 including thruster units for orientation and altitude maintenance located on the apexes of the frame. 
     
     
       16. The space station as set forth in claim 15 including at least one module secured to an apex of said frame. 
     
     
       17. A method of establishing a space station in earth orbit comprising the steps of: fabricating a framework formed of three full area, planar trusses constructed of a plurality of struts;   collapsing each truss to form a bundle;   transporting said bundles into earth orbit in the payload bay of the Space Shuttle Orbiter;   deploying said bundles in said orbit; and   expanding said bundles into a structurally stiff triangular framework.   
     
     
       18. The method as set forth in claim 17 wherein said step of expanding said bundles includes the step of simultaneously expanding said trusses in three-dimensional translation. 
     
     
       19. The method as set forth in claim 18 wherein said trusses are each tetrahedrals and said method of three-dimensional deployment includes orienting said trusses in a generally co-planar configuration, connecting said three trusses along juxtaposed edges and simultaneously expanding said trusses. 
     
     
       20. The method as set forth in claim 17 wherein the packaged framework includes three bundles, one for each truss, which are pivotally connected, and the bundles after deployment are rotated about the pivots into a co-planar configuration prior to expansion.